EP3374262B1 - Structures d'aube de rotor - Google Patents

Structures d'aube de rotor Download PDF

Info

Publication number
EP3374262B1
EP3374262B1 EP16864758.4A EP16864758A EP3374262B1 EP 3374262 B1 EP3374262 B1 EP 3374262B1 EP 16864758 A EP16864758 A EP 16864758A EP 3374262 B1 EP3374262 B1 EP 3374262B1
Authority
EP
European Patent Office
Prior art keywords
port
pressure
fluid channel
rotor blade
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16864758.4A
Other languages
German (de)
English (en)
Other versions
EP3374262A1 (fr
EP3374262A4 (fr
Inventor
Justin Thomas
Krzysztof KOPANSKI
Mark W. Scott
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sikorsky Aircraft Corp
Original Assignee
Sikorsky Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sikorsky Aircraft Corp filed Critical Sikorsky Aircraft Corp
Publication of EP3374262A1 publication Critical patent/EP3374262A1/fr
Publication of EP3374262A4 publication Critical patent/EP3374262A4/fr
Application granted granted Critical
Publication of EP3374262B1 publication Critical patent/EP3374262B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/64—Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7266—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators
    • B64C2027/7272—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated by actuators of the electro-hydraulic type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency

Definitions

  • the present disclosure relates to rotor blade assemblies, more specifically to rotor blade assemblies having trailing edge devices (e.g., flaps) or other actuated mechanisms.
  • trailing edge devices e.g., flaps
  • trailing edge (TE) devices can be used that move relative to the blade.
  • Certain TE devices include pneumatically driven valves.
  • the inclusion of TE devices and the supporting pneumatic conduits in traditional blades add complexity to manufacture and maintenance.
  • US 6 196 796 B1 discloses an actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex.
  • the actuation system includes a fluid supply which is connected to first and second fluid supply lines.
  • the fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator.
  • the actuator includes a housing mounted within the rotor blade and having a channel formed in it.
  • a butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes.
  • a first port connects the first fluid supply line with two diametrically opposed lobes in the channel.
  • a second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel.
  • a torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap.
  • the pressurization of the first fluid supply line causes the torque coupling to rotate in a first direction.
  • the pressurization of the second supply fluid line causes the torque coupling to rotate in the opposite direction.
  • a closeout structure for a rotor blade includes a first fluid channel having a first port which supplies a first pressure to the TE device via the first port, a second fluid channel having a second port which supplies a second pressure to the TE device via the second port, and a trough which forms a seal between the first and second channels.
  • the closeout structure forms a double-W shape as specified in claim 1.
  • the first and second W-shaped members can be adhered together.
  • the first W-shaped member can include at least one hole in the first and second fluid channels for ports to fluidly communicate the first and second fluid channels and the ports.
  • the closeout structure can have a length as long as a blade interior of the rotor blade.
  • the first channel can be sealed at a tip end and the second fluid channel can be sealed at a root end.
  • a rotor blade includes a trailing edge (TE) device disposed within the rotor blade and configured to operate with a differential pressure, the TE device including a first port and a second port.
  • the rotor blade includes a cavity extending at least a portion of the length of the rotor blade.
  • the rotor blade further includes a closeout structure as described herein disposed in the cavity.
  • the rotor blade can include a valve which selectively opens and closes the first and/or second ports to selectively activate the TE device.
  • a rotorcraft includes a plurality of rotor blades as described above.
  • the rotorcraft can further include a controller which controls the TE by selectively applying differential pressure via the first fluid channel and the second fluid channel.
  • the rotorcraft can include a valve which selectively opens and closes the first and/or second ports to selectively activate the TE device.
  • FIG. 1A an illustrative view of an embodiment of a blade in accordance with the disclosure is shown in Fig. 1A and is designated generally by reference character 100.
  • FIGs. 1B-3 Other embodiments and/or aspects of this disclosure are shown in Figs. 1B-3 .
  • the systems and methods described herein can be used to provide a differential pressure to a trailing edge (TE) device.
  • TE trailing edge
  • a rotor blade 100 can include a trailing edge (TE) device 101 disposed within the rotor blade 100.
  • the TE device 101 can be configured to operate with a differential pressure.
  • the rotor blade 100 can define a cavity 102 (e.g., in an aft portion of blade 100 forward of the TE device 101).
  • the cavity 102 can be at least partially filled with core material 145 (also see core material 245 in Fig. 2B ), which can include any suitable material (e.g., foam).
  • a closeout structure 103 for a rotor blade 100 can include a first fluid channel 105a and a second fluid channel 105b.
  • the closeout structure 103 can be configured to fit within at least a portion of the cavity 102.
  • a trough 111 is disposed between the first fluid channel 105a and the second fluid channel 105b such that the closeout structure 103 forms a double-W shape.
  • the core material 145 can be shaped to
  • the first fluid channel 105a is configured to supply a first pressure fluid to a first port 207 of the TE device 101.
  • the second fluid channel 105b is configured to supply a second pressure fluid to a second port 209 of the TE device 101, with a pressure differential between the first and second pressures powering the TE device 101.
  • the first fluid channel 105a can convey a higher pressure to the first port 207 than that conveyed to the second port 209 by the second fluid channel 105b, and the fluid can be air.
  • the first fluid channel 105a can be in fluid communication with a root pressure opening 117 at a root portion of the blade 100 which has a relatively high pressure during operation.
  • the second fluid channel 105b can be in fluid communication with a tip pressure opening 119 at the tip of the blade 100 which has a relatively low pressure during operation. In this manner, the first channel can be sealed at a tip end of the blade 100 and the second fluid channel can be sealed at a root end of the blade 100.
  • a differential pressure valve 213 of the TE device 101 can actuate a TE device effector (e.g., flap 215) when a suitable differential pressure acts on the valve 213 between the ports 207, 209 (e.g., due to a differential pressure between the root and the tip of the blade 100 when rotating).
  • Electrical components 223 can be operatively connected to the TE device 101 to selectively control the valve 213 (e.g., via a suitable controller 259 disposed on the blade 100. on the rotor hub 303 as shown in Fig. 3 , and/or in the fuselage 301 as shown in Fig. 3 such as in a flight control computer) to actuate in response to a differential pressure.
  • the closeout structure 103 can be defined by a first W-shaped member 103a and a second W-shaped member 103b.
  • the second W-shaped member 103b can be nested at least partially within the first W-shape member 103a to form the double W-shape.
  • the second W-shaped member 103b can have a shallower second member trough than a first member trough of the first W-shaped member 103a such that the first and second fluid channels 105a, 105b are formed between the first W-shaped member 103a and the second W-shaped member 103b.
  • the first member trough can bottom out on the second member trough, thereby sealing the first and second fluid channels 105a, 105b.
  • Each W-shaped member 103a, 103b can be made of composite material (e.g., carbon fiber) and/or include any other suitable material (e.g., aluminum sheet metal).
  • the first and second W-shaped members 103a, 103b can be adhered/bonded together at any suitable portion thereof (e.g., along the side walls, along the trough, and/or any other location), or assembled in any other suitable manner. Any other suitable arrangement to form the double W-shape is contemplated herein.
  • the closeout structure 103 can be made as a single piece (e.g., via casting or additive manufacturing), or out of any other suitable number of components.
  • the closeout structure 103 can be connected to the inside of the blade 100 in any suitable manner (e.g., via adhesive, via TE device nut plates 225). As shown in Fig. 2A , the nut plates 225 can be positioned aft of the closeout structure 103. However, as shown in Fig. 2B , the nut plates 225a can be moved forward (toward leading edge of blade 100) forward of fluid channels 105a, 105b. Placing the nut plates 225a forward can assist in resisting negative impact of local bending forces. It is contemplated that the blade 100 can be formed integrally with the closeout structure 103.
  • the first W-shaped member 103a can include at least one hole in the first and second fluid channels 105a, 105b for ports 207, 209 to fluidly communicate the first fluid channel 105a and the port 207, and second fluid channel 105b and the port 209.
  • a suitable seal 221 can be disposed within the holes and around each port 207, 209 to seal the channels 105a, 105b from the cavity 102.
  • the closeout structure 103 can have a length as long as a blade interior (e.g., the cavity 102) of the rotor blade 100.
  • a rotorcraft 300 can include a plurality of rotor blades 100 as described above attached to a rotor hub 303 which is rotatable connected to a fuselage 301.
  • the rotor blades 100 can include a TE device and closeout structure 103 as described above. While the rotorcraft 300 is shown as a single rotor helicopter, any suitable rotorcraft can employ one or more blades 100 as described above. By way of example, aspects of the invention can be used in coaxial helicopters, on tail rotors, or wings or propeller blades on fixed or tilt wing aircraft.
  • the two channels 105a, 105b provide the valve of the TE device 101 with access to high and low pressure air.
  • the trough 111 provides space for the electrical components 223 (e.g., wires and connectors).
  • Traditional designs do not support integration of a TE device 101 including conduits for wires and sources for pressure.
  • the double-W geometry of the closeout structure 103 as described above is a low weight and effective solution to this problem.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Structure (103) d'enveloppe pour une aube de rotor (100) ayant un dispositif de bord de fuite (TE) (101), la structure (103) d'enveloppe comprenant :
    un premier canal de fluide (105a) ayant un premier port (207) qui est conçu pour fournir une première pression au dispositif de TE (101) via le premier port (207) ;
    un second canal de fluide (105b) ayant un second port (209) qui est conçu pour fournir une seconde pression au dispositif de TE (101) via le second port (209) ; et
    un conduit (111) qui forme un scellement entre le premier canal de fluide (105a) et le second canal de fluide (105b), dans laquelle la structure (103) d'enveloppe est définie par un premier élément en forme de W (103a) et un second élément en forme de W (103b) inséré au moins en partie dans le premier élément en forme de W (103a) pour former une double forme de W, dans laquelle le second élément en forme de W (103b) a un conduit de second élément davantage peu profond qu'un conduit de premier élément du premier élément en forme de W (103a) de sorte que les premier et second canaux de fluide (105a, 105b) soient formés entre le premier élément en forme de W (103a) et le second élément en forme de W (103b).
  2. Structure (103) selon la revendication 1, dans laquelle les premier et second éléments en forme de W (103a, 103b) adhèrent ensemble.
  3. Structure (103) selon l'une quelconque des revendications 1 ou 2, dans laquelle le premier élément en forme de W (103a) inclut au moins un trou dans les premier et second canaux de fluide (105a, 105b) pour des ports (207, 209) pour faire communiquer de manière fluidique les premier et second canaux de fluide (105a, 105b) et les ports (207, 209).
  4. Structure (103) selon l'une quelconque des revendications précédentes, dans laquelle la structure (103) a une longueur aussi longue qu'un intérieur d'aube de l'aube de rotor (100).
  5. Structure (103) selon l'une quelconque des revendications précédentes, dans laquelle le premier canal de fluide (105a) est scellé à une extrémité d'aube de l'aube de rotor (100) et ouvert à un pied d'aube de l'aube de rotor (100) et le second canal de fluide (105b) est scellé au pied d'aube de l'aube de rotor (100) et ouvert à l'extrémité d'aube de l'aube de rotor (100).
  6. Aube de rotor (100), comprenant :
    un profil d'aile ayant un bord d'attaque et un bord de fuite et qui se prolonge depuis un pied d'aube jusqu'à une extrémité d'aube, le profil d'aile ayant une cavité (102) se prolongeant au moins au niveau d'une partie d'une longueur du profil d'aile entre le pied d'aube et l'extrémité d'aube ;
    un dispositif de bord de fuite (TE) (101) disposé dans l'aube de rotor (100) sensiblement au niveau du bord de fuite et conçu pour fonctionner avec une pression différentielle, le dispositif de TE (101) incluant un premier port (207) et un second port (209) ; et
    une structure (103) d'enveloppe selon l'une des revendications précédentes disposée dans la cavité (102), comprenant :
    le premier canal de fluide (105a) permettant de fournir la première pression au premier port (207) du dispositif de TE (101) ;
    le second canal de fluide (105b) permettant de fournir la seconde pression au second port (209) du dispositif de TE (101), la seconde pression étant différente de la première pression pour créer la pression différentielle.
  7. Aube (100) selon la revendication 6, comprenant en outre une vanne (213) qui ouvre et ferme de manière sélective les premier et/ou second ports (207, 209) pour activer de manière sélective le dispositif de TE (101).
  8. Giravion (300), comprenant :
    un fuselage (301) ;
    un moyeu de rotor (303) disposé de manière rotative sur le fuselage (301) ; et
    une pluralité d'aubes de rotor (100) reliées au moyeu de rotor (303), chaque aube (100) incluant :
    un dispositif de bord de fuite (TE) (101) disposé dans l'aube de rotor (100) sensiblement au niveau du bord de fuite et conçu pour fonctionner avec une pression différentielle, le dispositif de TE (101) incluant un premier port (207) et un second port (209) ; et
    une structure (103) d'enveloppe selon l'une des revendications 1 à 5 disposée dans la cavité (102), comprenant :
    le premier canal de fluide (105a) permettant de fournir la première pression au premier port (207) du dispositif de TE (101) ;
    le second canal de fluide (105b) permettant de fournir la seconde pression au second port (209) du dispositif de TE (101), la seconde pression étant différente de la première pression pour créer la pression différentielle.
  9. Giravion (300) selon la revendication 8, comprenant en outre un dispositif de commande (259) qui commande le dispositif de TE (101) en appliquant de manière sélective une pression différentielle via le premier canal de fluide (105a) et le second canal de fluide (105b).
  10. Giravion (300) selon l'une quelconque des revendications 8 ou 9, comprenant en outre une vanne (213) qui ouvre et ferme de manière sélective les premier et/ou second ports (207, 209) pour activer de manière sélective le dispositif de TE (101).
EP16864758.4A 2015-11-09 2016-10-25 Structures d'aube de rotor Active EP3374262B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201562252741P 2015-11-09 2015-11-09
PCT/US2016/058564 WO2017083089A1 (fr) 2015-11-09 2016-10-25 Structures d'aube de rotor

Publications (3)

Publication Number Publication Date
EP3374262A1 EP3374262A1 (fr) 2018-09-19
EP3374262A4 EP3374262A4 (fr) 2019-10-09
EP3374262B1 true EP3374262B1 (fr) 2021-02-24

Family

ID=58695923

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16864758.4A Active EP3374262B1 (fr) 2015-11-09 2016-10-25 Structures d'aube de rotor

Country Status (3)

Country Link
US (1) US20180319492A1 (fr)
EP (1) EP3374262B1 (fr)
WO (1) WO2017083089A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112249300B (zh) * 2020-10-22 2022-02-15 航天特种材料及工艺技术研究所 一种碳纤维复合材料翼面前缘结构

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3155166A (en) * 1962-09-17 1964-11-03 Parsons Corp Rotor blade including improved attachment of filled aft structure
GB1006111A (en) * 1963-03-06 1965-09-29 Hughes Tool Co Rotor blade for rotary-winged aircraft
US3765124A (en) * 1972-07-19 1973-10-16 United Aircraft Corp Helicopter rotor blade
US4275994A (en) * 1978-04-03 1981-06-30 Textron, Inc. Roll formed blade structure
US6200096B1 (en) * 1999-04-16 2001-03-13 Sikorsky Aircraft Corporation Actuation system for an active rotor control system
US6196796B1 (en) * 1999-04-22 2001-03-06 Sikorsky Aircraft Corporation High torque actuation system for an active rotor control system
DE10026018C2 (de) * 2000-05-25 2002-11-21 Daimler Chrysler Ag Kipp- bzw. Drehpositionierungsmittel
US6863239B2 (en) * 2003-02-27 2005-03-08 General Dynamics Advanced Information Systems, Inc. Fluid conduit for use with hydraulic actuator
US20060049302A1 (en) * 2004-08-31 2006-03-09 Kennedy Dennis K Apparatus and methods for structurally-integrated conductive conduits for rotor blades
US7611090B2 (en) * 2005-12-20 2009-11-03 The Boeing Company Reaction-drive rotorcraft having an adjustable blade jet
US7708229B1 (en) * 2006-03-22 2010-05-04 West Virginia University Circulation controlled airfoil
GB2467945B (en) * 2009-02-20 2014-03-05 Westland Helicopters Device which is subject to fluid flow
US8939395B2 (en) * 2010-09-09 2015-01-27 Groen Brothers Aviation, Inc. Tail fan apparatus and method for low speed yaw control of a rotorcraft
US9133819B2 (en) * 2011-07-18 2015-09-15 Kohana Technologies Inc. Turbine blades and systems with forward blowing slots
US9446843B2 (en) * 2012-03-27 2016-09-20 The Boeing Company Enhanced performance rotorcraft rotor blade
EP3025030B1 (fr) * 2013-07-24 2021-04-21 Raytheon Technologies Corporation Joint à rainure destiné à un moteur à turbine à gaz

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2017083089A1 (fr) 2017-05-18
US20180319492A1 (en) 2018-11-08
EP3374262A1 (fr) 2018-09-19
EP3374262A4 (fr) 2019-10-09

Similar Documents

Publication Publication Date Title
EP2808253B1 (fr) Hélicoptère avec ventilateur à écoulement transversal
EP3299290B1 (fr) Agencement de rotor orientable rotatif pour aéronef à rotors basculants
US10183745B2 (en) Tiltrotor with inboard engines
US10167078B2 (en) Rotary or fixed wing aircraft with thrust vectoring tail
US7918415B2 (en) Convertible aircraft operating method
EP0937641B1 (fr) Surfaces de commande avec compensation automatique
US9505492B2 (en) Mission adaptive rotor blade
EP1957363B1 (fr) Systeme de commande de giravion et procede d'utilisation correspondant
EP2821343B1 (fr) Système de commande hydraulique indépendant pour rotor secondaire de giravion
EP2581304B1 (fr) Refrodissement d'un composant d'une pale de rotor
CN103097244A (zh) 翼型尾梁
US10486806B2 (en) Pivot systems for tiltwing aircraft
US10112697B2 (en) Aircraft with thrust vectoring tail
US10538311B2 (en) Propeller diverter duct
US10023304B2 (en) Tail rotor actuation system
EP3374262B1 (fr) Structures d'aube de rotor
CN102887222A (zh) 一种扭角分布可变的桨叶
EP3564130B1 (fr) Turbine à air dynamique hybride comprenant une pompe hydraulique et un générateur en ligne
EP3103718B1 (fr) Pale de rotor à plusieurs éléments
JP6845746B2 (ja) 航空機のヨー制御
US20180319487A1 (en) Rotorcraft configuration
US20030132341A1 (en) Device by a horizontally and vertically flying aircraft
EP2487108B1 (fr) Dispositif modulaire intégré pour le contrôle d'une pale de rotor
EP0937642A2 (fr) Surfaces de commande avec compensation automatique
EP3072814A1 (fr) Pale pour rotor anticouple d'helicopter avec palier en composite

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180604

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20190910

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/72 20060101ALI20190904BHEP

Ipc: B64C 3/18 20060101ALN20190904BHEP

Ipc: B64C 27/46 20060101ALI20190904BHEP

Ipc: B64C 27/473 20060101AFI20190904BHEP

Ipc: B64C 27/64 20060101ALI20190904BHEP

Ipc: B64C 27/59 20060101ALI20190904BHEP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602016053334

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: B64C0027720000

Ipc: B64C0027473000

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/59 20060101ALI20200730BHEP

Ipc: B64C 3/18 20060101ALN20200730BHEP

Ipc: B64C 27/473 20060101AFI20200730BHEP

Ipc: B64C 27/64 20060101ALI20200730BHEP

Ipc: B64C 27/72 20060101ALI20200730BHEP

Ipc: B64C 27/46 20060101ALI20200730BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20200910

RIN1 Information on inventor provided before grant (corrected)

Inventor name: THOMAS, JUSTIN

Inventor name: SCOTT, MARK W.

Inventor name: KOPANSKI, KRZYSZTOF

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602016053334

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1364143

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210315

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210524

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210525

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210524

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210624

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1364143

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602016053334

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

26N No opposition filed

Effective date: 20211125

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210624

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20211031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211025

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211031

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20161025

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231027

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20231023

Year of fee payment: 8

Ref country code: FR

Payment date: 20231025

Year of fee payment: 8

Ref country code: DE

Payment date: 20231027

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210224